Consider a helicopter with the following properties: 1. Using Cp Weight Main Rotor Tipspeed Main Rotor Radius Number of Blades Engine Power Transmission Loss F/A Flight Path Angle CdO Empirical Correction Factor Divergence Mach Number KCT2 σcdo 2√12+22 8 16000 lbs 725 ft/s 27 ft 4 3000 HP 10% 0.015 5 degrees 0.008 1.15 0.96 + ººº (1 + 4.65µ²) +¾½µ³ ²+λCT, calculate the max speed in knots for steady level flight from sea level to 25000 feet while keeping the blade tip speed under the divergence Mach number. Use the ratio of density at altitude to sea level density as a knockdown factor to the available engine power. 2. Using the above equation for the same altitude range and constraints, find the new max speed while ensuring that the helicopter can climb at the service ceiling rate. a. Solve using a climb velocity of 100 ft/min in the power equation b. Solve using the leftover power divided by weight to get 100 ft/min 3. Compare the two different max speeds from step 2.
Consider a helicopter with the following properties: 1. Using Cp Weight Main Rotor Tipspeed Main Rotor Radius Number of Blades Engine Power Transmission Loss F/A Flight Path Angle CdO Empirical Correction Factor Divergence Mach Number KCT2 σcdo 2√12+22 8 16000 lbs 725 ft/s 27 ft 4 3000 HP 10% 0.015 5 degrees 0.008 1.15 0.96 + ººº (1 + 4.65µ²) +¾½µ³ ²+λCT, calculate the max speed in knots for steady level flight from sea level to 25000 feet while keeping the blade tip speed under the divergence Mach number. Use the ratio of density at altitude to sea level density as a knockdown factor to the available engine power. 2. Using the above equation for the same altitude range and constraints, find the new max speed while ensuring that the helicopter can climb at the service ceiling rate. a. Solve using a climb velocity of 100 ft/min in the power equation b. Solve using the leftover power divided by weight to get 100 ft/min 3. Compare the two different max speeds from step 2.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
Related questions
Question
Recall that power available at altitude is (rho/rho0)*power at sea level. Include transmission losses!
[~, a, ~, RHO, ~] = atmosisa(alt(k1)*0.3048);
rho=RHO*0.0685218/35.3147;
rho_scale=rho/rho0;
a=a/0.3048;
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